In-flight refueling system and method for facilitating emergency separation of in-flight refueling system components

ABSTRACT

An in-flight refueling system and method are provided for facilitating the emergency separation of the components of a probe and drogue in-flight refueling. The in-flight refueling system and method provides a fuse device capable of being installed between, for instance, an elongate hose configured to trail from a tanker aircraft, and a drogue connected to, and in fluid communication with, the elongate hose. The fuse device may be configured to separate in response to a separating force such that the drogue may separate from the elongate hose prior to the exertion of a damaging force, a non-certified force, or an unknown aerodynamic force on the elongate hose, on a probe carried by a second receiver aircraft, or on the tanker aircraft.

FIELD OF THE INVENTION

The present invention relates generally to in-flight refueling of amanned or unmanned aircraft using a probe and drogue in-flight refuelingsystem, and specifically, providing a mechanical fuse device configuredto safely and predictably separate two components of an in-flightrefueling system. More particularly the mechanical fuse device andmethod of the present invention provide a mechanical fuse having a knownyield point for use in an in-flight refueling system such that shouldthe in-flight refueling system be subjected to tension or shear forcesin excess of the yield point of the mechanical fuse device themechanical fuse may separate in a controlled manner so as to minimizedamage to other components of the in-flight refueling system.

BACKGROUND OF THE INVENTION

In-flight refueling (or air-to-air refueling) is an important method forextending the range of both manned and unmanned aircraft traveling longdistances over areas having no feasible landing or refueling points.Although in-flight refueling is a relatively common operation,especially for military aircraft, the passage of large amounts of fuelbetween a first aircraft (serving, for example, as a tanker aircraft)and second aircraft during an in-flight refueling operation may create apotentially dangerous situation, especially if components of thein-flight refueling system separate and/or fail in an uncontrolledmanner.

One conventional system for in-flight refueling is the probe and droguein-flight refueling system wherein the tanker aircraft may extend aflexible hose having an end attached to a drogue such that the secondaircraft having a refueling probe, may engage the drogue while in flightin order to initiate the transfer of fuel. An operator of the secondaircraft is responsible for maneuvering the second aircraft such thatthe refueling probe extending therefrom may enter and engage the drogue.According to some conventional probe and drogue in-flight refuelingsystems, the engagement of the refueling probe with the drogue isaccomplished as the second aircraft accelerates with respect to thetrailing drogue. The drogue may include, for, instance, a catchmechanism for securing the refueling probe within the drogue so that therefueling probe may be securely fastened within the drogue during thetransfer of fuel.

At the conclusion of the in-flight refueling operation, the operator ofthe second aircraft may control the second aircraft such that the secondaircraft may decelerate with respect to the trailing drogue such that aseparating force is exerted on the refueling probe such that therefueling probe may be disengaged from the drogue and/or the catchmechanism within the drogue. The operator of the second aircraft isresponsible for decelerating the second aircraft in a controlled mannerso as to safely disengage the refueling probe from the drogue withoutintroducing excessive tension or shear forces to the trailing hose orcomponents of the in-flight refueling system that may be disposed withina fuselage of the tanker aircraft or in a pod hanging, for instance, ona wing hardpoint of the tanker aircraft. In some cases, however, thecatch mechanism within the trailing drogue may malfunction such that therefueling probe may not be disengaged from the trailing drogue withoutsubjecting the hose and/or other in-flight refueling system componentsto an excessive tension or shear force.

In such cases, conventional probe and drogue in-flight refueling systemsmay provide a guillotine system disposed, for instance, in the fuselageof the tanker aircraft, for jettisoning the hose from the tankeraircraft. More particularly, a guillotine blade may be configured to becapable of cutting the hose at a point inside or near the fuselage ofthe tanker aircraft such that the hose may fall away from the tankeraircraft. In addition, the guillotine may block the fuel conduit definedwithin the remaining length of hose and may further, in cooperation withfuel shut-off valves disposed within the tanker aircraft, preventadditional fuel from flowing from the tanker aircraft. If the guillotinesystem is used, however, the jettisoned portion of the hose may stillhang from the refueling probe of the second aircraft such that a longsection of loose hose may be left trailing from the refueling probe.Such a situation may be extremely dangerous for the operator of thesecond aircraft, as the remaining section of hose may oscillateuncontrollably with respect to the second aircraft and may strike andshatter a windscreen of the second aircraft or strike and damage acontrol surface of the second aircraft. Additionally, if the secondaircraft is a jet powered aircraft, the remaining section of hose may bedrawn into a jet intake of the second aircraft and damage one or more ofthe engines of the second aircraft.

If the catch mechanism of the drogue malfunctions as described above,the operators of the first and second aircraft, may also confer anddecide to attempt to land the first and second aircraft in unison so asto prevent the need for jettisoning the hose. This option, however, mayalso be extremely dangerous, given the precision required to maintainthe second aircraft in a position relative to the tanker aircraft so asto safely land the aircraft in unison. In addition, this option may notbe available if, for instance, the in-flight refueling operation isunderway far away from an available airfield. It is this situation thatpresents the need to conduct in-flight refueling operations in the firstplace. In addition, such a landing may be impossible in cases where thefirst and second aircraft may have significantly different stallcharacteristics.

Thus, it would be advantageous to provide an alternative method fordisengaging the hose and/or drogue from a refueling probe of a secondaircraft should the refueling probe of the second aircraft be unable tobe safely disengaged from the drogue during an in-flight refuelingoperation. In addition, it would be advantageous to provide a separatingmechanism that may separate the drogue from the hose carried by thetanker aircraft in a controlled and predictable manner so as to avoidthe dangerous situations described in more detail above. It would beespecially advantageous to provide a separating mechanism disposedbetween an end of the hose and the drogue of a probe and droguein-flight refueling system such that upon the exertion of a separatingforce, the hose may separate from the drogue such that a severed portionof hose may be less likely to hang from the refueling probe (and thedrogue attached thereto) of the second aircraft. Thus, the secondaircraft may safely extract itself from a refueling connection with thetanker aircraft leaving only the drogue attached to the refueling probe.

Therefore, there exists a need for a mechanical fuse device and methodfor facilitating controlled separation of in-flight refueling systemcomponents that may be installed in a probe and drogue in-flightrefueling system. More particularly, there exists a need for amechanical fuse device that may be disposed between selected componentsof a probe and drogue in-flight refueling system such that themechanical fuse device may be configured to be capable of separating ina controlled and predictable manner such that a second aircraft maysafely disengage from the probe and drogue in-flight refueling systemcarried by a tanker aircraft even in cases where, for instance, anin-flight refueling probe carried by the second aircraft may not becapable of disengaging from a drogue trailing from the tanker aircraft.

SUMMARY OF THE INVENTION

The embodiments of the present invention satisfy the needs listed aboveand provide other advantages as described below. The in-flight refuelingsystem and method of the present invention provide for the controlledemergency separation of probe and drogue in-flight refueling systemcomponents in response to a separating force. More particularly, thein-flight refueling system according to one embodiment of the presentinvention comprises: a tanker aircraft; an elongate hose having a firstend carried by the tanker aircraft and a drogue operably engaged withand in fluid communication with an opposing second end of the elongatehose; and a fuse device operably engaged between a first end of theelongate hose and the drogue so as to allow fluid communicationtherebetween. The fuse device may be configured to disengage the droguefrom the elongate hose in response to a separating force experiencedthereby. The fuse device may also be further configured to be separableinto a first segment operably engaged with a first portion of theelongate hose and a second segment operably engaged with the drogue inresponse to a separating force experienced by the fuse device. Thus, thein-flight refueling system may allow the drogue to be separable from thefirst portion of the elongate hose in response to the separating force.Furthermore, in some embodiments, the fuse device may be positionedbetween the second end of the hose and the drogue such that the fusedevice may be capable of separating into a first segment operablyengaged with the second end of the elongate hose and a second segmentoperably engaged with the drogue in response to a separating forceexperienced thereby, such that the drogue may be separable from thesecond end of the elongate hose in response to the separating force.

The fuse device provided as part of the in-flight refueling system maybe further configured such that the separating force is less than abreakage force required to damage the elongate hose. Furthermore,according to other embodiments, fuse device provided as part of thein-flight refueling system of the present invention may further comprisea first threaded portion configured to be capable of operably engaging afirst threaded surface disposed on the second end of the elongate hose;and a second threaded portion configured to be capable of operablyengaging a second threaded surface disposed on the drogue such that theelongate hose and drogue may be connected and in fluid communication viathe fuse device.

The embodiments of the present invention also provide a method forfacilitating the emergency separation of a drogue from an elongate hosewherein the drogue and elongate hose are operably engaged and in fluidcommunication via a fuse device as part of an in-flight refuelingsystem. The method, according to one embodiment of the presentinvention, may comprise the steps of: exerting a separating force on thedrogue; and disengaging the drogue from elongate hose at the fuse devicein response to a separating force exerted on the elongate hose and thedrogue, such that the first portion of the elongate hose is separablefrom the drogue in response to the separating force. According to somemethod embodiments, the disengaging step may further comprise separatingthe fuse device into a first segment operably engaged with the elongatehose and a second segment operably engaged with the drogue in responseto the separating force experienced thereby. According to otheradvantageous embodiments, the method of the present invention mayfurther comprise the step of blocking a flow of fuel through theelongate hose so as to prevent the flow of fuel from exiting theelongate hose via the first segment.

Thus the various embodiments of the in-flight refueling system andmethod of the present invention provide many advantages that mayinclude, but are not limited to: providing a disengageable and/orseparable fluid connection between an elongate hose and a drogue as partof a probe and drogue in-flight refueling system such that the drogueand hose may separate at a predictable point in response to a separatingforce exerted between a tanker aircraft carrying the elongate hose anddrogue and a second aircraft carrying a refueling probe configured toengage the drogue; providing a fuse device that may be easily connectedto both the elongate hose and the drogue such that a replacement fusedevice may be installed in the probe and drogue in-flight refuelingsystem following an emergency separation of the in-flight refuelingsystem components; and minimizing the chance that the elongate hose maybe severed by the separating force so as to minimize the likelihood thata severed portion of the elongate hose may be attached to a refuelingprobe carried by a second aircraft.

These advantages and others that will be evident to those skilled in theart are provided in the in-flight refueling system and method of thepresent invention.

BRIEF DESCRIPTION OF THE DRAWINGS

Having thus described the invention in general terms, reference will nowbe made to the accompanying drawings, which are not necessarily drawn toscale, and wherein:

FIG. 1 shows an elongate hose and attached drogue extending from atanker aircraft according to one embodiment of the present invention anda second aircraft carrying a refueling probe approaching the tankeraircraft;

FIG. 2 shows a partial cross-section of a fuse device according to oneembodiment of the present invention wherein the fuse device is disposedbetween an elongate hose and a drogue as part of a probe and droguein-flight refueling system;

FIG. 3 shows a fuse device according to one embodiment of the presentinvention wherein the cross section of the fuse device is minimized at achannel defined in an outer surface of the fuse device;

FIG. 4 shows a fuse device according to one embodiment of the presentinvention wherein the first and second portions of the fuse device areconnected via at least one shear bolt at a junction;

FIG. 5 shows an in-flight refueling system according to one embodimentof the present invention wherein the fuse device has been separated inresponse to a separating force so that the elongate hose is separatedfrom the drogue; and

FIG. 6 shows a partial cross-section of a connection between theelongate hose and the drogue wherein the fuse device comprises one ormore shear bolts configured to directly connect the elongate hose to thedrogue.

DETAILED DESCRIPTION OF THE INVENTION

The present inventions now will be described more fully hereinafter withreference to the accompanying drawings, in which some, but not allembodiments of the invention are shown. Indeed, these inventions may beembodied in many different forms and should not be construed as limitedto the embodiments set forth herein; rather, these embodiments areprovided so that this disclosure will satisfy applicable legalrequirements. Like numbers refer to like elements throughout.

While the in-flight refueling system and method embodiments of thepresent invention are described below in the context of a fuse device120 disposed between an elongate hose 112 and a drogue 114, it should beunderstood that the embodiments of the present invention may also beutilized to achieve the controlled and predictable separation of avariety of in-flight refueling system components that may be subjectedto a separation force during the course of an in-flight refuelingoperation, including, but not limited to, connections between a tankeraircraft 110 and an end of the elongate hose 112, connections betweenadjacent and separable portions of elongate hose 112, connectionsbetween a fuel reservoir and a probe and drogue in-flight refuelingsystem carried by a tanker aircraft 110 and other fluid connectionsbetween in-flight refueling system components that may require safelycontrolled and predictable separation when subjected to a separatingforce. It should also be understood that the embodiments of the presentinvention may also be utilized in in-flight refueling systems other thanprobe and drogue refueling systems, such as, for instance boom in-flightrefueling systems and/or wing-mounted pod-based probe and droguein-flight refueling systems.

FIG. 1 shows a schematic view of a probe and drogue in-flight refuelingoperation wherein a tanker aircraft 110 is shown carrying and extendingan elongate hose 112 having a first end (not shown) carried by (and influid communication with a fuel reservoir onboard) the tanker aircraft110 and a drogue 114 operably engaged with and in fluid communicationwith an opposing second end 113 of the elongate hose 112. The first endof the elongate hose 112 may be operably engaged with a hose take-upassembly (such as a roller drum) carried by the tanker aircraft 110, andthe second end 113 of the elongate hose 112 and the drogue 114 operablyengaged therewith way be configured to be taken up into a tunnelor/other aperture defined in a fuselage of the tanker aircraft 110 asthe hose take-up assembly retracts the elongate hose 112. Also shown inFIG. 1 is a second aircraft 130 carrying a refueling probe 132configured to enter and become operably engaged with the drogue 114 soas to enable fuel to pass from the tanker aircraft 110 through theelongate hose 112 to the second aircraft 130 as part of an in-flightrefueling operation. An operator of the second aircraft (either, forinstance, an on-board operator or a remote operator in the case of anunmanned aircraft (UAV)) is responsible for positioning the secondaircraft 130 with respect to the drogue 114 such that the refuelingprobe 132 may enter and engage the drogue 114. Also shown is a fusedevice 120, disposed between the second end 113 of the elongate hose 112and the drogue 114 so as to allow fluid communication between theelongate hose 112 and the drogue 114. The fuse device 120, in someembodiments, may be disposed between the second end 113 of the elongatehose 112 and the drogue 114 in a low-profile arrangement (as showngenerally in FIG. 2) such that the fuse device 120 may be taken up intothe tunnel or other aperture defined in a fuselage of the tankeraircraft 110 as the hose take-up assembly retracts the elongate hose112. Furthermore, the fuse device 120 is configured to disengage thedrogue from the elongate hose in response to a separating forceexperienced thereby, such that the elongate hose is separable from thedrogue in response to the separating force. More particularly, in someembodiments, the fuse device 120 may be separable into a first segment120 a operably engaged with the second end 113 of the elongate hose 112and a second segment 120 b operably engaged with the drogue 114 inresponse to a separating force experienced by the fuse device 120. Thus,according to the embodiments of the present invention, the drogue 114may be separable from the second end 113 of the elongate hose 112 inresponse to the separating force (as shown in FIG. 5). Although the fusedevice 120 is shown to be between the second end 113 of the elongatehose 112 and the drogue 114, the fuse device 120 may be positionedelsewhere along the hose such that the fuse device 120 is disposedbetween two portions of the elongate hose 112, thereby allowing the twoportions of the elongate hose 112 to be separable in a similar mannerwhen subjected to the separating force.

FIG. 2 shows a more detailed view of the fuse device 120 and itsdisposition between the elongate hose 112 and the drogue 114. The fusedevice 120 may define, for instance, a fuel conduit 220 therein suchthat fuel may pass from the second end 113 of the elongate hose 112through the first and second segments 120 a, 120 b, and through thedrogue 114 to a refueling probe 132 (see FIG. 1) carried by a secondaircraft 130. An interior of the drogue 114 may further comprise, forinstance, a catch mechanism 250 configured to be capable of securing therefueling probe 132 carried by the second aircraft 130 after theoperator of the second aircraft 130 has positioned the second aircraft130 such that the refueling probe 132 enters the drogue 114.Furthermore, one skilled in the art will appreciate that the operator ofthe second aircraft 130 may also be responsible for disengaging therefueling probe 132 from the drogue 114 at the conclusion of thein-flight refueling operation by, for instance, decelerating withrespect to the tanker aircraft 110 so as to exert a tension force on thedrogue 114 and the catch mechanism 250 that holds the refueling probe132 within the drogue 114. In some cases, however, the catch mechanism250 may malfunction such that the operator of the second aircraft 130may be unable to disengage the refueling probe 132 from the drogue 114without exerting an excessive tension force on the drogue 114 andattached elongate hose 112 carried by the tanker aircraft 110. Suchtension forces may, in some cases, be transferred along the elongatehose 112 and into a fuselage of the tanker aircraft 110 to, forinstance, a rotating drum hose take-up assembly. Such tension forces mayalso, if allowed to continue, tear or break the elongate hose 112 at anunpredictable point along the length of the elongate hose 112.

Thus, according to embodiments of the present invention, as shown inFIG. 2, the fuse device 120 may comprise a separable portion 210disposed between the first and second segments 120 a, 120 b andconfigured to be capable of failing (by, for instance, an elasticfailure or after a substantially plastic deformation) in response to apredetermined tension force such that the fuse device 120 may separateinto a first segment 120 a that may remain attached to the second end113 of the elongate hose 112 and a second segment 120 b that may remainattached to the drogue 114 in response to a separating force (such as,for example, a predetermined tension force) experienced by the fusedevice 120. According to some embodiments, the separating force may bepredetermined such that the separating force may be less than a breakageforce required to damage the elongate hose 112.

The fuse device 120 may be connected to the elongate hose 112 and, inthe illustrated embodiment, to the drogue 114 in any manner known tothose skilled in the art. As shown in FIG. 2, however, some embodimentsof the in-flight refueling system of the present invention may comprisea fuse device 120 including a first threaded portion 212 configured tobe capable of operably engaging a first threaded surface 230 disposed onthe second end 113 of the elongate hose 112 and a second threadedportion 214 configured to be capable of operably engaging a secondthreaded surface 240 disposed on the drogue 114. According to otherembodiments, the fuse device may be configured so as to be capable ofoperably engaging the second end 113 of the elongate hose 112 and thedrogue 114 by a variety of other connection mechanisms and techniquesthat may include, but are not limited to, bolts, rivets, adhesives,clamps, frictional press-fit components, and/or other mechanisms thatmay be suitable for connecting the fuse device 120 with the second end113 of the elongate hose 112 as well as with the drogue 114 so as to bedisposed between the elongate hose 112 and the drogue 114 and to allowfluid communication therebetween. In other instances, the fuse device120 may be operably engaged with the second end 113 of the elongate hose112 and the drogue 114 by a first connection mechanism as describedabove and also operably engaged therewith via a redundant safetymechanism (such as a safety wire connection) such that the fuse device120 is connected to the elongate hose 112 and, in the illustratedembodiment, to the drogue 114 in a manner that is sufficiently securesuch that the separating force required to cause the separable portion210 to fail is less than that required to cause the connections of thefuse device 120 to the elongate hose 112 and drogue 114 to fail. Inaddition, regardless of the type of connection, the fuse device 120 isadvantageously connected to the elongate hose 112 and, in theillustrated embodiment, to the drogue 114 in a manner that issufficiently secure such that the separating force required to cause theseparable portion 210 to fail is less than that required to cause theconnections of the fuse device 120 to the elongate hose 112 and drogue114 to fail, thereby ensuring that the separable portion 210 may failwhile the opposed first and second segments 120 a, 120 b of the fusedevice 120 remain coupled to the elongate hose 112 and the drogue 114.

Thus, in advantageous embodiments of the present invention, should thefuse device 120 be separated into the first segment 120 a and the secondsegment 120 b by, for instance, a separating force exerted during anin-flight refueling operation, both the tanker aircraft 110 and thesecond aircraft 130 may land safely with the elongate hose 112 anddrogue 114 still attached respectively thereto (see FIG. 5, depictingthe fuse device 120 after separation into first and second segments 120a, 120 b). After the tanker aircraft 110 and the second aircraft 130have safely landed, a technician may examine the first and secondsegments 120 a, 120 b, and subsequently remove them from the second endof the elongate hose 112 and the drogue 114, respectively. Thus, thetechnician may then simply insert a new fuse device 120 into adisposition between the second end 113 of the elongate hose 112 and thedrogue 114 so that the probe and drogue in-flight refueling system maybe returned to operational status in a relatively quick procedure whencompared to repairs and/or inspections that must be completed inconventional probe and drogue in-flight refueling systems wherein theelongate hose 112 has been torn, sheared, and/or broken by a separatingforce. The technician may also, in some cases, examine the drogue 114and its associated catch mechanism 250 in order to attempt to determinethe cause for the catch mechanism's 250 failure to release the refuelingprobe 132 upon the exertion of a tension force exceeding the separationforce that caused, for instance, the separation of the fuse device 120into first and second segments 120 a, 120 b. Upon examination and/or asubsequent investigation of the catch mechanism 250, the technician mayalso repair and/or replace the drogue 114 and its associated catchmechanism 250 when replacing the fuse device 120.

As shown in FIGS. 1 and 2, and as described generally above, the fusedevice 120 may comprise a separable portion 210 configured to be capableof failing in response to a separating force such that the fuse device120 may separate into a first segment 120 a that may remain attached tothe second end 113 of the elongate hose 112 and a second segment 120 bthat may remain attached to the drogue 114 in response to the separatingforce experienced by the fuse device 120. The first and second segmentsmay be composed of for instance, a metal, metallic alloy, polymer,composite material, or other material suitable for maintainingstructural integrity as the adjacent separable portion 210 is allowed tocontrollably fail as described in more detail below. As shown in FIG. 3the separable portion 210 may comprise a channel defined in the fusedevice 120, wherein the channel is formed so as to purposely weaken thefuse device 120 such that the fuse device 120 will fail at a predictablepoint (the channel (or separable portion 210), for instance) in responseto the applied separating force. According to some embodiments, thechannel may be defined in an outer surface of the fuse device 250 (asshown in FIG. 3). In other embodiments, the channel may be defined in aninner surface of the fuse device 120. One skilled in the art willappreciate that the separable portion 210 of the fuse device 120 maycomprise a pair of complementary channels defined in the inner and outersurfaces of the fuse device 120 so long as a fuel conduit may bemaintained between the adjacent portions of the in-flight refuelingsystem that may be connected by the fuse device 120. In addition,according to other embodiments, the separable portion 210 of the fusedevice 120 may further comprise a material configured to failelastically or after deforming in a substantially plastic mode prior tothe failure of the first segment 120 a, the second segment 120 b, theelongate hose 112, or other components of the in-flight refuelingsystem. The material used to produce the separable portion 210 maycomprise, for instance, a metal, metallic alloy, polymer, compositematerial, or other material suitable for failing in a controlled andpredictable manner in response to the separating force.

Furthermore, according to other embodiments of the present invention asshown generally in FIG. 4, the fuse device 120 may comprise a firstsegment 120 a and a second segment 120 b attached by the separableportion 210, wherein the separable portion 210 may comprise, forinstance, a connector, such as one or more shear bolts 210 c. In someinstances, the first and second segments 120 a, 120 b may comprise firstand second flanges 210 a, 210 b, respectively, that may be configured toreceive and retain a connector, such as, for instance a shear bolt 210c. In such embodiments, the shear bolt 210 c may be configured to failelastically or after deforming in a substantially plastic mode prior tothe failure of the first segment 120 a, the second segment 120 b, theelongate hose 112, or other components of the in-flight refuelingsystem, such that the first segment 120 a may be separable from thesecond segment 120 b in response to a separating force having amagnitude sufficient to cause the failure of the shear bolt 210 c. Oneskilled in the art will appreciate that other types of deformable and/orseparable connectors may also be used to connect the first and secondsegments 120 a, 120 b of the fuse device 120 at a junction such as, forinstance, the separable portion 210. Additionally, in such embodiments,a gasket or other sealing device may be disposed at substantiallybetween the first and second segments 120 a, 120 b so as to seal thefluid conduit defined between the first and second segments 120 a, 120 bof the fuse device 120. Thus, in embodiments of the in-flight refuelingsystem of the present invention comprising one or more shear bolts 210 cconfigured to connect the first and second segments 120 a, 120 b of thefuse device 120 at a separable portion 210.

While the illustrated embodiment of FIG. 4 depicts the fuse device 120having separable first and second segments 120 a, 120 b connected by aseparable portion 210, the fuse device 120 may also comprise one or moreshear bolts 210 c configured to directly connect the second end 113 ofthe elongate hose 112 to the drogue 114 so as to allow fluidcommunication between the elongate hose 112 and the drogue 114 via afuel conduit 220 defined therein. In such embodiments, as shown in FIG.6, the shear bolt 210 c may comprise a separable portion 210 disposedalong a shaft of the shear bolt 210 c such that the shear bolt 210 c (ormultiple shear bolts) may controllably and predictably fail in responseto the separating force exerted thereon such that the drogue 114 may bereleased from the second end 113 of the elongate hose 112 leaving forinstance, a first segment 120 a of the shear bolt 210 c operably engagedwith the elongate hose 112 and a second segment 120 b of the shear bolt210 c operably engaged with the drogue 114.

Also according to some embodiments of the present invention, the fusedevice need not separate into a first and second segment 120 a, 120 b inorder to effectively disengage the drogue 114 from the elongate hose112. In some instances, the fuse device 120 may be operably engagedbetween the elongate hose 112 and the drogue 114 so as to allow fluidcommunication therebetween, and the fuse device 120 may be configured todisengage the drogue 114 from the elongate hose 112 in response to aseparating force experienced thereby, such that the elongate hose 112may be separable from the drogue 114 in response to the separatingforce. In some embodiments, after the separating force is exerted, thefuse device 120 may be left operably engaged with the second end 113 ofthe elongate hose 112. In other embodiments, the fuse device 120 mayremain operably engaged with the drogue 114 after the separating forceis applied. In either case, the fuse device 120 is configured to retainthe elongate hose 112 in operable engagement (and fluid communication)with the drogue 114 in response to a tension force up to a level that isequal to or greater than the separating force required to cause thedisengagement of the fuse device 120. For instance, in some embodiments,the second segment 120 b may be configured to be capable of disengagingfrom the drogue 114 wherein no portion of the shear bolt 210 c (or otherfuse device 120) may remain operably engaged with the drogue after thedisengagement of the drogue 114 from the second end 113 of the elongatehose 112. For example, the second portion 120 b of the shear bolt 210 cmay comprise a head of the shear bolt 210 c that may be released uponthe disengagement of the drogue 114 from the second end 113 of theelongate hose 112. In addition, according to other embodiments, the fusedevice 120 may comprise an adhesive material, magnetic device, or othermaterial and/or mechanism suitable for selectively and directly engagingthe second end 113 of the elongate hose 112 with the drogue 114 suchthat the drogue 114 may be disengaged from the second end 113 of theelongate hose 112 in response to the separating force wherein no portionof the fuse device 120 may remain operably engaged with the disengageddrogue 114.

FIG. 5 shows an in-flight refueling system according to one embodimentof the present invention wherein the fuse device 120 (which is disposedbetween a second end 113 of the elongate hose 112 and the drogue 114carried by the tanker aircraft 110 as part of a probe and droguein-flight refueling system) has been separated into a first segment 120a operably engaged with the second end 113 of the elongate hose 112 anda second segment 120 b operably engaged with a drogue 114. As shown inFIG. 5 the drogue 114 (and the second segment 120 b of the fuse device120 operably engaged therewith) has been separated from the in-flightrefueling system due to, for instance, an emergency wherein a force atleast as great as the separating force has been applied to the fusedevice 120. Thus, the drogue 114 may be carried by, for instance, therefueling probe 132 of the second aircraft 130. While this arrangementis not optimal (as the drogue 114 may block the view of an operator ofthe second aircraft 130 as well as introduce aerodynamic disturbances tothe flight characteristics of the second aircraft 130), the secondaircraft may still, however, land safely with the drogue 114 carriedthereby without the danger of a portion of the elongate hose 112 beingattached to the drogue 114 and possibly striking the second aircraft 130or being drawn into a jet intake of the second aircraft 130. Inaddition, the first segment 120 a of the fuse device 120 is shownoperably engaged with the second end 113 of the elongate hose 112. Uponthe separation of the fuse device 120, an operator of the in-flightrefueling system carried by the tanker aircraft 110 may prevent a flowof fuel through the elongate hose, by, for instance, actuating a fuelshut-off valve (not shown) that may be disposed within a fuselage of thetanker aircraft 110 so as to prevent the passage of fuel through theelongate hose 112 and out into the open air via the separated firstsegment 120 a of the fuse device 120. In addition, the in-flightrefueling system carried by the tanker aircraft 110 may further comprisea guillotine device configured to jettison the elongate hose 112 (andthe first segment 120 a of the fuse device 120 attached thereto) if, forinstance, the in-flight refueling system is incapable of safelyretracting the elongate hose 112 into a fuselage of the tanker aircraft110.

Referring again to FIG. 1, the embodiments of the present invention alsoprovide a method for facilitating the emergency separation of a drogue114 from an elongate hose 112 wherein the drogue 114 and elongate hose112 are operably engaged and in fluid communication via a fuse device120 disposed therebetween as part of an in-flight refueling system. Themethod may comprise the steps of exerting a separating force on thedrogue 114 (such as by inserting a refueling probe 132 carried by asecond aircraft 130 into the drogue 114 and subsequently deceleratingthe second aircraft 130 with respect to the moving drogue 114; anddisengaging the drogue 114 from elongate hose 112 at the fuse device 120in response to a separating force exerted on the elongate hose 112 andthe drogue 114, such that the first portion of the elongate hose may beseparable from the drogue 114 in response to the separating force. Inother embodiments of the method of the present invention, thedisengaging step may further comprise the step of separating the fusedevice 120 into a first segment 120 a operably engaged with the elongatehose 112 and a second segment 120 b operably engaged with the drogue 114in response to the separating force exerted on the drogue 114. Accordingto other embodiments, the method of the present invention may furthercomprise blocking a flow of fuel through the elongate hose 112 so as toprevent the flow of fuel from exiting the elongate hose 112 via thefirst segment 120 a. This blocking step may be accomplished by, forinstance, actuating a fuel control valve carried by the tanker aircraft110 so as to shut off the flow of fuel through the in-flight refuelingsystem. Furthermore, according to other embodiments, the separating step(described in more detail above) may further comprise separating thefuse device 120 using a separating force that is less than a breakageforce required to damage the elongate hose 112. Thus, the fuse device120 may fail prior to the breakage of the elongate hose 112 so as toprevent the unpredictable and possibly violent breakage of the elongatehose 112 and/or other components of the in-flight refueling systemcarried by the tanker aircraft 110.

Many modifications and other embodiments of the invention will come tomind to one skilled in the art to which this invention pertains havingthe benefit of the teachings presented in the foregoing descriptions andthe associated drawings. Therefore, it is to be understood that theinvention is not to be limited to the specific embodiments disclosed andthat modifications and other embodiments are intended to be includedwithin the scope of the appended claims. Although specific terms areemployed herein, they are used in a generic and descriptive sense onlyand not for purposes of limitation.

1. An in-flight refueling system comprising: a tanker aircraft; anelongate hose having a first end carried by the tanker aircraft and adrogue operably engaged with and in fluid communication with an opposingsecond end thereof; and a fuse device operably engaged between the firstend of the elongate hose and the drogue so as to allow fluidcommunication therebetween, the fuse device being configured todisengage the drogue from the elongate hose in response to a separatingforce experienced thereby, such that the elongate hose is separable fromthe drogue in response to the separating force.
 2. An in-flightrefueling system according to claim 1, wherein the fuse device isfurther configured to be separable into a first segment operably engagedwith a first portion of the elongate hose and a second segment operablyengaged with the drogue in response to a separating force experiencedthereby, such that the first portion of the elongate hose is separablefrom the drogue in response to the separating force.
 3. An in-flightrefueling system according to claim 1, wherein the fuse device isoperably engaged between the second end of the elongate hose and thedrogue such that the fuse device is further configured to be separableinto a first segment operably engaged with the second end of theelongate hose and a second segment operably engaged with the drogue inresponse to a separating force experienced thereby, such that the drogueis separable from the second end of the elongate hose in response to theseparating force.
 4. An in-flight refueling system according to claim 1,wherein the fuse device is further configured such that the separatingforce is less than a breakage force required to damage the elongatehose.
 5. An in-flight refueling system according to claim 1, wherein thefuse device is selected from the group consisting of: at least one shearbolt; a cylindrical conduit; and combinations thereof.
 6. An in-flightrefueling system according to claim 1, wherein die fuse device furthercomprises: a first threaded portion configured to be capable of operablyengaging a first threaded surface disposed on the second end of theelongate hose; and a second threaded portion configured to be capable ofoperably engaging a second threaded surface disposed on the drogue. 7.An in-flight refueling system adapted to be carried by a tankeraircraft, comprising: an elongate hose having a first end carried by thetanker aircraft and a drogue operably engaged with and in fluidcommunication with an opposing second end thereof; and a fuse deviceoperably engaged between the first end of the elongate hose and thedrogue so as to allow fluid communication therebetween, the fuse devicebeing configured to disengage the drogue from the elongate hose inresponse to a separating force experienced thereby, such that theelongate hose is separable from the drogue in response to the separatingforce.
 8. An in-flight refueling system according to claim 7, whereinthe fuse device is further configured to be separable into a firstsegment operably engaged with a first portion of the elongate hose and asecond segment operably engaged with the drogue in response to aseparating force experienced thereby, such that the first portion of theelongate hose is separable from the drogue in response to the separatingforce.
 9. An in-flight refueling system according to claim 7, whereinthe fuse device is operably engaged between the second end of theelongate hose and the drogue such that the fuse device is furtherconfigured to be separable into a first segment operably engaged withthe second end of the elongate hose and a second segment operablyengaged with the drogue in response to a separating force experiencedthereby, such that the drogue is separable from the second end of theelongate hose in response to the separating force.
 10. An in-flightrefueling system according to claim 7, wherein the fuse device isfurther configured such that the separating force is less than abreakage force required to damage the elongate hose.
 11. An in-flightrefueling system according to claim 7, wherein the fuse device isselected from the group consisting of: at least one shear bolt; acylindrical conduit; and combinations thereof.
 12. An in-flightrefueling system according to claim 7, wherein the fuse device furthercomprises: a first threaded portion configured to be capable of operablyengaging a first threaded surface disposed on the second end of theelongate hose; and a second threaded portion configured to be capable ofoperably engaging a second threaded surface disposed on the drogue. 13.A method for facilitating the emergency separation of a drogue from anelongate hose wherein the drogue and elongate hose are operably engagedand in fluid communication via a fuse device disposed therebetween aspart of an in-flight refueling system, the method comprising: exerting aseparating force on the drogue; and disengaging the drogue from elongatehose at the fuse device in response to a separating force exerted on theelongate hose and the drogue, such that the first portion of theelongate hose is separable from the drogue in response to the separatingforce.
 14. A method according to claim 13, wherein the disengaging stepfurther comprises separating the fuse device into a first segmentoperably engaged with the elongate hose and a second segment operablyengaged with the drogue in response to the separating force experiencedthereby.
 15. A method according to claim 13, further comprising blockinga flow of fuel through the elongate hose so as to prevent the flow offuel from exiting the elongate hose via the first segment.
 16. A methodaccording to claim 13, wherein the disengaging step further comprisesdisengaging the drogue from the elongate hose at the fuse device using aseparating force that is less than a breakage force required to damagethe elongate hose.